Disc turbine engine

Abstract

A disc turbine engine includes a multi disc engine in which each disc engine includes a turbine blade, and low-pressure compressor blade, a high-pressure compressor blade and a bearing that runs the disc engine freely around a shaft. Each disc engine has its own cooling system, the compressor's blades act as cooling fins for the turbine blade, and air bleeding from the high-pressure compressor to the lower pressure compressor through a hollow turbine blade. Cooling the nozzle is by attaching the nozzle to the guide fan and by air bleeding through the hollow body. There is no stator in between the disc engine and no large shaft is required because the power produced by each turbine blade is consumed by its own compressor. The weight and cost of this engine will be less than other engines at the same thrust output.

The invention claimed is: 
     
       1. A disc turbine engine comprising:
 a front fan, a low-pressure compressor section containing at least one low-pressure compressor, a high-pressure compressor section containing at least one high-pressure compressor, a turbine section containing at least one turbine, a combustion chamber, a nozzle, an exhaust nozzle, a guide vane, and a multi-disc engine; 
 said multi-disc engine is constructed with at least two discs; 
 each disc of the at least two discs comprising:
 a bearing surrounded by a high-pressure compressor of the at least one high-pressure compressor, said high-pressure compressor comprising at least one high-pressure compressor blade, 
 said high-pressure compressor surrounded by a turbine of the at least one turbine, said turbine comprising at least one turbine blade, 
 said turbine surrounded by a low-pressure compressor of the at least one low pressure compressor, said low-pressure compressor comprising at least one low-pressure compressor blade, 
 said bearing, said high-pressure compressor, said turbine and said low-pressure compressor of each disc of the at least two discs configured in a concentric planar disc; 
 
 a fixed shaft that holds said multi-disc engine in a housing; 
 a fan shaft that is located around said fixed shaft and is connected to a first disc of the at least two discs, said fan shaft being connected to said front fan with a gear; and 
 a first air is bled from the high-pressure compressor section of the disc turbine engine into the at least one high-pressure compressor blade of the at least one disc of the at least two discs, the first air traveling through the high-pressure compressor blade of the at least one disc of the at least two discs into the at least one turbine blade of the at least one disc of the at least two discs and into the at least one low-pressure compressor blade of the at least one disc of the at least two discs. 
 
     
     
       2. The disc turbine engine according to  claim 1 ,
 wherein said fixed shaft has a first channel and a second channel; 
 said first channel is for oil feeding through said bearing of each disc of the at least two discs, and said second channel is for a return of said oil from said bearing of each disc of the at least two discs. 
 
     
     
       3. The disc turbine engine according to  claim 2 ,
 wherein at least a portion of said first channel and a portion of said second channel are located in front of said front fan to intercool said oil in said first channel and said second channel. 
 
     
     
       4. The disc turbine engine according to  claim 1 ,
 wherein said disc turbine engine does not include a stator between any consecutive discs of said at least two discs. 
 
     
     
       5. The disc turbine engine according to  claim 1 ,
 wherein said nozzle is located in front of the respective turbine of the first disc of the at least two discs, 
 said guide vane is located in front of the respective low-pressure compressor of the first disc of the at least two discs, and 
 the nozzle is connected to the guide vane as one hollow body. 
 
     
     
       6. The disc turbine engine according to  claim 5 ,
 wherein a second air which has passed through the high-pressure compressor section of the disc turbine engine is bled through the nozzle and into the guide vane. 
 
     
     
       7. The disc turbine engine according to  claim 6 , wherein said guide vane acts as a fin to cool said nozzle. 
     
     
       8. The disc turbine engine according to  claim 1 ,
 wherein a second air which has exited the low-pressure compressor section of the disc turbine engine runs through at least one pipe and into a hollow body of the exhaust nozzle and into said high-pressure compressor section. 
 
     
     
       9. The disc turbine engine according to  claim 8 ,
 wherein the second air flowing inside said at least one pipe and into the hollow body of said exhaust nozzle absorbs energy from exhaust gas and increases a pressure of the second air flowing inside the at least one pipe. 
 
     
     
       10. The disc turbine engine according to  claim 1 ,
 wherein the first air in the at least one low-pressure compressor blade of the at least one disc of the at least two discs is injected into the low-pressure compressor section of the disc turbine engine. 
 
     
     
       11. The disc turbine engine according to  claim 1 , wherein said disc turbine engine is a turbo jet engine. 
     
     
       12. The disc turbine engine according to  claim 1 , wherein said disc turbine engine is a turbofan engine. 
     
     
       13. The disc turbine engine according to  claim 1  wherein said disc turbine engine is a turbo shaft engine. 
     
     
       14. The disc turbine engine according to  claim 1 , wherein the bearing of each disc of the at least two discs is connected to the fixed shaft. 
     
     
       15. The disc turbine engine according to  claim 1 ,
 wherein each disc of the at least two discs runs freely and individually from the other discs of the at least two discs and 
 each disc of the at least two discs is counter-rotating.